Aircraft controls



JO 3 13330 A. F. VRNJE 1,892,916

AIRCRAFT CONTROLS Filed March 19, 1950 IKNE IF VIN/E BY mFoRNEY a p E citer latest data AIRCRAFT C(JNTROLS Application filed March 19, 1930. Serial No. 436,967.

This invention relates to aircraft controls and is illustrated as applied to the controls for the rudder of an airplane.

Prior to my invention there have been proposed devices for controlling rudders of air planes. The devices actually used therefor have usually been of one of two classes. Either a rudder bar in the form of a wall:- ing beam has been used or pedals have been used. In some circumstances, pedals are more advantageous than rudder bars. Pedals are usually operated in vertical planes substantially parallel to the sides of the fuselage, while the movement of the foot in operating a rudder bar is along a substantially horizontal curved path. Pedals are therefore more convenient and more comfortable for the pilot. Moreover, pedals provide more free space in certain parts of the cockpit than rudder bars. Furthermore, it is easier to design Wheel brakes to be used in combination with pedals than with rudder bars.

Where pedals are used for the control of the rudder, it is ad 'antageous that some means be provided for maintaining the rudder cables taut in order to aid the ilotin attaining more accurate steering. rior to my invention springs have possibly been provided pulling against the rudder cables, but the springs previously used, it any, have been subject to the disadvantage that inequalities therein affect the neutral position of the rudder and to the further disadvantage that they opposed steering and make the control of the 35 airplane more difficult.

One of the objects of my invention is the provision in combination with pedal controls for a rudder. of means for maintaining the control cables taut.

40 A further object of my invention is the provision in combination, with pedal controls for the rudder of an airplane. of means for maintaining the rudder cables taut while not increasing the diiliculties of steering.

A further object of my invention is the elimination of spring resistance which may be encountered in the operation of pedal controls for a rudder of an airplane.

Further objects will be apparent from a reading of the subjoined specification. and 59 claims and from a consideration of the accompanying drawing.

In order to explain the invention more clearly, two embodiments thereof are shown in said drawing, in which:

Fig. 1 is a side elevation of a device nsel. for illustration of my invention;

Fig. 2 is a rear elevation of the device illustrated in Fig. 1;

Fig. 3 is a plan View of the device t in Figs. 1 and 2: and

Fig. 4: is a plan view similar to showing a slightly di'lierent modification il lustrative of my invention.

In general, the devices used for illustration of my invention comprise a pair of pedals each connected to a rudder cable for operating the rudder and for controlling the movement of the airplane about its vertical axis. Combined with these elements are To means for holding the rudder cables taut. These last means are so arranged that the do not interfere with or retard the operation of the pedals for moving the rudder.

Referring specifically to the drawing illustrating my invention I have shown a pair of pedals 11 and 12 to which are secured the fittings 13 and 14, respectively. The fitting 13 is connected to a rudder cable 15 and the fitting 14 is connected to a rudder cable 16. The rudder pedal 11 comprises a foot bar 1.7 carried by a pair of parallel arms 18 and 19 which are in turn supported by a sleeve 20 mounted for rotation about a pivot rod 21. The rudder pedal 12 similarly comprises a foot bar 9 carried by parallel arms 23 and Qet secured to a sleeve 25 similarly pivoted on the bar 21. Supports 26 and 27 are provided for the rod 21. Thus, movement of the pedals 11 and 12 about the pivot rod 21 causes a corresponding pull on the cables 15 and 16 and a turning movement of the rudder to control the airplane.

Means are provided for maintaining the cables 15 and 16 taut at all times. The sleeve 20 carries on the side thereof opposite to the pedal 11 a lever arm 28. To the outer end of the lever arm 28 there is fastened a spring 29. The opposite end of the spring 29 is fastened as at 31 to one end of a walking beam 32 pivoted at 33 to a part 34 of the stationary structure of the airplane. The opposite end 35 of the walking beam 32 is connected to a spring 36 similar to the spring 29, and the opposite end of the spring 36 is connected to a lever arm 37 (similar to the arm 28) fastened to the sleeve 25 opposite to the rudder pedal 12.

In the operation of this embodiment of my invention movement of either of the pedals 11 or 12 forward causes a corresponding pull upon the cable 15 or 16 as previouslysu ggested and therefore operates the rudder of the airplane. lVhether the pedals 11 and 12 are being operated or not, the springs 29 and 36 constantly pull on the arms 28 and 37 to maintain the pedals 11 and 12 in a forward position and thus maintain the cables 15 and 16 taut. However, when the pedals 11 and 12 are operated, the operation does not increase the tension of the springs 29 and 86, inasmuch as movement forward of one of the arms 28 and 37 is compensated for by movement backward of the other arm. Thus, there is no spring resistance to operation of the pedals 11 and '12 and though the controls are maintained taut, steering is no more difficult than it would he were there no springs interposed.

In Fig. 4 I have shown a different form of device illustrative of my invention. Therein pedals 11 and 12 include sleeves 20 and 25 mounted on the pivot rod 21.. The pedals carry fittings 13 and 14, respectively, and these fittings are connected to cables 15 and 16*, respectively. The fittings 13 and 14 are continued on the opposite side of the pedals from the cables 15 and 16 as at 38 and 39. Connected to the part 38 of the fitting 13" is a cable 41 Which passes forward around a pulley 42 and is connected as at 43 to a spring 44. The Opposite end of the spring 44 is connected as at 45 to a cable 46 passing around a pulley 47 and then rearward to be connected at 39 to the fitting 14.

This embodiment of my invention is operated in all respects similarly to theiemhodiment previously described. lvlovementpf the pedals 11 or 12 forward exerts a pull on the cables 15 or 16 and consequently controls movement of the rudder. The spring 44 constantly maintains the cables 15 and 16 taut, but inasmuch as the spring is freely floating between I the oppositely. moving pedals 11 and 12 it resiliently retaining the does not exert any retarding effect on the movement of the controls and no effort is required for stretching the spring when operating to move said controls.

It is to be understood that the above described embodiment of the invention is for the purpose of illustration only and various changes may be made therein without departing from the spirit and scope of the invention.

I claim as my invention:

1. In a system of controls for an aerial vehicle an axle, a pair of pedals pivoted thereon, a pair of cables connected to the said pedals, arms also connected to the said pedals and arranged on opposite sides of the said axle, springs connected to the said arms and interconnected by a walking beam pivoted on a line drawn longitudinally of the aerial vehicle intermediate the two arms.

2. In aircraft control apparatus, a rudder, a pair of rudder pedals, a pair of cables connected to said rudder and to said rudder pedals, and means outside of said cables for resiliently retaining said cables taut without interposing any resistance to movement of said pedals.

3. In a system of controls for an aerial vehicle, a rudder, a pair of rudder pedals, a pair of cables connected to said pedals and extended rearwardly therefrom to a connection to said rudder, a pair. of additional cables connected to said rudder pedals and extending forwardly therefrom, and balance means connected with both of said last named cables for resiliently retaining the first mentioned cables taut.

4. In a system of aircraft controls, a control surface, levers for operating said control surface, a plurality of undivided cables each extending uninterruptedly between said control surface and said control levers, and means including a transverse beam for resiliently maintaining said cables taut without interposing any resistance to movement of the control levers.

5. In a system of aircraft controls, a. conto said levers for maintaining said cables taut without interposing any resistance to movement of the control levers,

6. In a system of controls for an aerial vehicle. a rudder, a pair of'rudder pedals, a pair of cables connected to said pedals and extended rearwardly therefrom to a connection tosaid rudder, a pair of additional cables connected to said rudder pedals and extending forwardly therefrom, and means connecting the free ends of said last named cables for first mentioned cable's-taut.

7. In a system of controls for an aerial vehicle, a rudder, a pair of rudder pedals, a pair of cables connected to said pedals and extending rearwardly therefrom to a connection to said rudder, a pair of additional cables connected to said rudder pedals and extending forwardly therefrom, and means including a pivotal member connected with both of said last named cables for resiliently retaining the first mentioned cables taut.

In testimony whereof I hereunto aflix my signature.

ARNE F. VINJE. 

